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公开(公告)号：US20230366548A1
公开(公告)日：2023-11-16
申请号：US17823198
申请日：2022-08-30
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Perumallu Vukanti , Ajoy Patra , Pradeep Naik , Hiranya Nath
IPC: F23R3/00
CPC classification number: F23R3/005
Abstract: A combustor for a gas turbine includes a combustor liner, an outer casing surrounding the combustor liner, an ignitor housing extending through an ignitor opening through the liner, and an ignitor disposed within the ignitor housing. The ignitor housing includes a housing wall including at least one airflow inlet passage on a downstream side of the housing wall and arranged within the outer flow passage, and at least one cooling passage on the downstream side within the housing wall. The at least one cooling passage extends along a length of the ignitor housing from the at least one airflow inlet passage and through the inner end of the ignitor housing, the at least one cooling passage being in fluid communication with the at least one airflow inlet passage.
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公开(公告)号：US11815269B2
公开(公告)日：2023-11-14
申请号：US17586082
申请日：2022-01-27
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Manampathy G. Giridharan , Ajoy Patra , Pradeep Naik , R Narasimha Chiranthan , Perumallu Vukanti , Michael T. Bucaro
IPC: F23R3/28
CPC classification number: F23R3/286
Abstract: A turbine engine that includes an engine core having at least a compressor section and a combustion section. The combustion section includes a combustor. The combustor section or combustor includes a fuel-air mixing assembly fluidly coupled to the compressor section. The fuel-air mixing assembly includes an outer wall, a center body at least partially circumscribed by the outer wall, and an annular flow passage between the outer wall and center body. At least one fuel orifice includes a fuel outlet fluidly coupled to the annular flow passage.
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公开(公告)号：US11761632B2
公开(公告)日：2023-09-19
申请号：US17394848
申请日：2021-08-05
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Karthikeyan Sampath , Perumallu Vukanti , Allen M. Danis , Scott M. Bush , Steven Clayton Vise , Hari Ravi Chandra , Rimple Rangrej , Saket Singh , Pradeep Naik , Neeraj Kumar Mishra , Arvind Kumar Rao , Balasubramaniam Venkatanarayanan , Ranjeet Kumar Mishra
Abstract: A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.
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公开(公告)号：US20230243502A1
公开(公告)日：2023-08-03
申请号：US17717603
申请日：2022-04-11
Applicant: GENERAL ELECTRIC COMPANY
Inventor： R Narasimha Chiranthan , Manampathy G. Giridharan , Ajoy Patra , Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Hiranya Kumar Nath
Abstract: A turbine engine can include a compressor section, a combustion section, and a turbine section in serial flow arrangement. The combustion section can include a combustor with a fuel mixer. The fuel mixer can include an outer wall defining a longitudinal direction and having a mixture outlet, a first compressed air flow passage, and a second compressed air flow passage.
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公开(公告)号：US11692708B1
公开(公告)日：2023-07-04
申请号：US17809379
申请日：2022-06-28
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Perumallu Vukanti , Ajoy Patra , Pradeep Naik , Hiranya Nath
CPC classification number: F23R3/14 , F23R3/06 , F23R2900/03044
Abstract: A combustor liner for a gas turbine includes a liner that at least partially defines a combustion chamber, and that a plurality of dilution openings therethrough. Each dilution opening includes an outer wall defining an outer perimeter of the dilution opening and defining a dilution opening centerline axis through the dilution opening. A plurality of swirl vanes extend from the outer wall into a dilution airflow passage that extends through the dilution opening. Each of the plurality of swirl vanes extends from the outer wall into the dilution airflow passage at a respective swirl vane angle with respect to the outer wall. The plurality of swirl vanes are arranged in a successive arrangement about the outer wall, and successive respective ones of the plurality of swirl vanes extend from the outer wall at a different swirl vane angle.
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Patent Agency Ranking
公开(公告)号：US20230204215A1
公开(公告)日：2023-06-29
申请号：US17675270
申请日：2022-02-18
Applicant: General Electric Company
Inventor： Pradeep Naik , Ajoy Patra , Michael T. Bucaro , Perumallu Vukanti , Steven C. Vise , Michael A. Benjamin , Manampathy G. Giridharan , Saket Singh , Clayton S. Cooper
CPC classification number: F23R3/286 , F02C7/22 , F23C7/004 , F23D17/002 , F23L7/002 , F23R3/14 , F23R3/36
Abstract: An engine can utilize a combustor to combust fuel to drive the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. The fuel nozzle assembly can be configured to increase lateral provision of fuels to reduce flame scrubbing on combustor liners for the combustor.
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公开(公告)号：US20230204213A1
公开(公告)日：2023-06-29
申请号：US17691781
申请日：2022-03-10
Applicant: General Electric Company
Inventor： Pradeep Naik , Perumallu Vukanti , Michael T. Bucaro , Ajoy Patra , Manampathy G. Giridharan , Steven C. Vise , Michael A. Benjamin , Sripathi Mohan , R Narasimha Chiranthan , Joseph Zelina
CPC classification number: F23R3/14 , F23R3/286 , F23D11/383
Abstract: A turbine engine can utilize a combustor to combust fuel to drive the turbine, which drives the engine. A fuel nozzle assembly can supply fuel to the combustor for combustion or ignition of the fuel. The fuel nozzle assembly can include a swirler and a fuel nozzle to supply a mixture of fuel and air for combustion. Increasing efficiency and carbon-containing emission needs benefit from the use of alternative fuels, which combust at higher temperatures than traditional fuels, requiring improved fuel introduction without the occurrence of flame holding or flashback.
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公开(公告)号：US11592182B1
公开(公告)日：2023-02-28
申请号：US17653384
申请日：2022-03-03
Applicant: General Electric Company
Inventor： Rimple Rangrej , Pradeep Naik , Perumallu Vukanti , Saket Singh
Abstract: A swirler assembly of a combustor of a gas turbine, the swirler assembly including a primary swirler having a primary swirler flow opening, and a swirler ferrule plate connected to an upstream side of the primary swirler. The swirler ferrule plate includes (a) a fuel nozzle opening, and (b) a plurality of oxidizer purge passages surrounding the fuel nozzle opening, each one of the plurality of oxidizer purge passages including (i) an inlet passage portion, and (ii) an outlet passage portion extended from the inlet passage portion to a downstream end of the swirler ferrule plate and having an outlet in fluid communication with the primary swirler flow opening. The outlet passage portion has an increasing cross-sectional area extending along the length of the outer passage portion from the inlet passage portion to the outlet that induces a pressure drop in a flow of oxidizer through the oxidizer flow passage.
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公开(公告)号：US20230042970A1
公开(公告)日：2023-02-09
申请号：US17394848
申请日：2021-08-05
Applicant: General Electric Company
Inventor： Gurunath Gandikota , Karthikeyan Sampath , Perumallu Vukanti , Allen M. Danis , Scott M. Bush , Steven Clayton Vise , Hari Ravi Chandra , Rimple Rangrej , Saket Singh , Pradeep Naik , Neeraj Kumar Mishra , Arvind Kumar Rao , Balasubramaniam Venkatanarayanan , Ranjeet Kumar Mishra
IPC: F23R3/14
Abstract: A dome assembly for a combustor includes: at least one swirler assembly including: at least one swirler including a plurality of swirl vanes arrayed about an axis, the plurality of swirl vanes oriented so as to impart a tangential velocity to air passing through the swirler parallel to the axis; each of the plurality of swirl vanes having a thickness and including a plurality of edges which collectively define a peripheral boundary of the respective swirl vane; wherein at least a selected one of the plurality of swirl vanes includes at least one void passing through the thickness of the selected swirl vane, the void disposed within the peripheral boundary of the selected swirl vane.
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公开(公告)号：US20220390115A1
公开(公告)日：2022-12-08
申请号：US17340856
申请日：2021-06-07
Applicant: General Electric Company
Inventor： Karthikeyan Sampath , Pradeep Naik , Veeraraju Vanapalli , Perumallu Vukanti , Shai Birmaher , Daniel J. Kirtley , Deepak Ghiya , Rimple Rakeshkumar Rangrej , Saket Singh , Ravindra Shankar Ganiger , Hiranya Kumar Nath , Michael Anthony Benjamin , Rajendra Mahadeorao Wankhade
Abstract: A combustor for a gas turbine engine, the gas turbine engine defining a longitudinal centerline extending in a longitudinal direction, a radial direction extending orthogonally outward from the longitudinal centerline, and a circumferential direction extending concentrically around the longitudinal centerline, the combustor including: a forward liner segment; an aft liner segment disposed downstream from the forward liner segment relative to a direction of flow through the combustor, the forward and aft liner segments at least partially defining a combustion chamber; and an intermediate member disposed at least partially between the forward and aft liner segments and extending in the circumferential direction.
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